Effect of Length of Handley Page Tip Slots on the Lateral-stability Factor, Damping in Roll PDF Download
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Author: Fred E. Weick
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 490
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Book Description
The optimum length of slot for satisfactory damping in roll over a large range of angles of attack was found to be slightly over 50 percent of the semispan for the form of slot tested.
Author: Fred E. Weick
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 490
Get Book Here
Book Description
The optimum length of slot for satisfactory damping in roll over a large range of angles of attack was found to be slightly over 50 percent of the semispan for the form of slot tested.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 596
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 860
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 616
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Book Description
Author: United States. Army. Air Service
Publisher:
ISBN:
Category :
Languages : en
Pages : 318
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 32
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 138
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category :
Languages : en
Pages : 312
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Book Description
Author: Fred E. Weick
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 694
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Book Description
Flight tests were made with a typical light airplane to investigate possibilities for obtaining reliable control at low flight speeds. It was found that satisfactory lateral control occurred consistently, even under conditions simulating extremely gusty air, at angles of attack approximately 2 degrees below that for the maximum lift coefficient (or the stall of the wing as a whole). This 2 degree margine was substantially the same both with full power and with the engine throttled and throughout the range of center-of-gravity locations tested. Supplementary tests were then made on the control at high angles of attack under actual gusty air conditions, on the possibility of entering spins, and on the amount of elevator control required for normal three-point landings. It was found that with the original plain untwisted wing obtaining the constant 2 degree margin below the stall required widely different elevator deflections for the range of power and center-of-gravity locations tested. Also, none of these settings ws high enough to produce a three-point landing.
